压气机近失速点的性能仿真及可转导叶的影响

Performance Simulation of Compressor Near Stall Point and Influence of the Inlet Guide Vane

压气机的不稳定边界包括失速边界和喘振边界,对压气机工作特性有着重大的影响,甚至会对其造成严重损害,所以研究清楚近失速点的流场有着重要的意义。本文以某2.5级跨音速轴流压气机为研究对象,运用CFX计算其在全工况七种转速下的特性线;重点研究近失速点的内部流场,对比近设计点与近堵塞点流场状态,探究多级轴流压气机的失速特性与失速机理。对可转导叶的角度进行调整,将叶片向着叶片前缘吸力面方向和相反方向旋转相同的角度,计算50%,80%,100%转速下的特性线,发现在中高转速下流量压比特性线向左下平移,效率压比特性线向左平移更为明显,说明将叶片向着叶片前缘吸力面方向旋转可以起到推迟失速发生的作用。

The unstable boundary of compressor include stall boundary and surge boundary which have an important influence on the compressor's characteristics,even cause serious damage to it,so making clear the internal flow field near stall pointhas important significance.This paper took a 2.5 stage transonic axial flow compressor as research object,the compressor's characteristic curves include all operating conditions at seven speeds were calculated by CFX.This paper focuses on the internal flow field near stall point,contrasts near the design point and near plug flow,explores the stall characteristics and mechanism of multistage axial compressor.Adjust the angle of the inlet guide vane,rotate the vane toward the suction surface of the front edge and the opposite direction by the same angle,calculate the characteristic line at 50%,80%and 100%design speed.It is not difficult to find out under the middle and high speed,the flow pressure characteristic line moves downward to the left,the efficiency pressure characteristic line moves more obviously.It comes to conclusion,the inlet guide vane rotates toward the suction of the front edge of the blade direction can delay stall.